Design of an Intake and a Thruster for an Atmosphere-Breathing Electric Propulsion System

TL;DR

This paper presents the design of an intake with high collection efficiency and a novel RF Helicon-based plasma thruster for atmosphere-breathing electric propulsion, enabling longer low-altitude space missions.

Contribution

It introduces a highly efficient intake design and a low-power plasma thruster tailored for atmosphere-breathing propulsion systems in VLEO missions.

Findings

Intake design achieves up to 94% collection efficiency.

The plasma thruster operates effectively with low input power (~60 W).

Demonstrates feasibility of atmosphere-breathing propulsion for extended VLEO missions.

Abstract

Challenging space missions include those at very low altitudes, where the atmosphere is source of aerodynamic drag on the spacecraft that finally defines the missions lifetime unless way to compensate for it is provided. This environment is named Very Low Earth Orbit (VLEO) and is defined for $h<450~km$. In addition to the satellite's aerodynamic design, to extend the lifetime of such missions an efficient propulsion system is required. One solution is Atmosphere-Breathing Electric Propulsion (ABEP) that collects atmospheric particles to be used as propellant for an electric thruster. The system would minimize the requirement of limited propellant availability and can also be applied to any planetary body with atmosphere, enabling new missions at low altitude ranges for longer times. One of the objectives of the H2020 DISCOVERER project, is the development of an intake and an electrode-less plasma thruster for an ABEP system. The article describes the characteristics of intake design and the respective final deigns providing collection efficiencies up to $94\%$. On the other side, the radio frequency (RF) Helicon-based plasma thruster (IPT) developed at IRS, is hereby presented as well, while its performances are being evaluated, the thruster has been operated with single atmospheric species as propellant, and has highlighted very low input power requirement for operation at comparable mass flow rates $P\sim 60~W$.